BRPI0418861A - upstream structure on a turbine or compressor device and method for assembling the structure - Google Patents

upstream structure on a turbine or compressor device and method for assembling the structure

Info

Publication number
BRPI0418861A
BRPI0418861A BRPI0418861-6A BRPI0418861A BRPI0418861A BR PI0418861 A BRPI0418861 A BR PI0418861A BR PI0418861 A BRPI0418861 A BR PI0418861A BR PI0418861 A BRPI0418861 A BR PI0418861A
Authority
BR
Brazil
Prior art keywords
inner ring
struts
support structure
cross sectional
sectional dimensions
Prior art date
Application number
BRPI0418861-6A
Other languages
Portuguese (pt)
Inventor
Gunnar Marke
Jan-Erik Andreasson
Bo Johansson
Original Assignee
Volvo Aero Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Volvo Aero Corp filed Critical Volvo Aero Corp
Publication of BRPI0418861A publication Critical patent/BRPI0418861A/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/11—Manufacture by removing material by electrochemical methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/12—Manufacture by removing material by spark erosion methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Abstract

The present invention relates to a support structure and a method for assembling a support structure in a turbine or compressor engine for rotatably supporting a rotor member in a stator member. The support structure includes an inner ring, an outer ring and a plurality of struts which extend radially between the inner ring and the outer ring. The inner ring has integrated portions projecting in the direction of the struts and forming end connections for the struts. The integrated end connecting portions of the inner ring are together with the ring made by a metal alloy having initially oversized cross sectional dimensions relative to the cross sectional dimensions of corresponding strut, followed by working at least one lateral surface for removing material. The purpose is to achieve final dimensions and position to conform to the cross sectional dimensions and correct position of each corresponding strut.
BRPI0418861-6A 2004-05-27 2004-05-27 upstream structure on a turbine or compressor device and method for assembling the structure BRPI0418861A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2004/000824 WO2005116405A1 (en) 2004-05-27 2004-05-27 A support structure in a turbine or compressor device and a method for assembling the structure

Publications (1)

Publication Number Publication Date
BRPI0418861A true BRPI0418861A (en) 2007-11-20

Family

ID=35450943

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0418861-6A BRPI0418861A (en) 2004-05-27 2004-05-27 upstream structure on a turbine or compressor device and method for assembling the structure

Country Status (8)

Country Link
US (1) US7544040B2 (en)
EP (1) EP1753938B1 (en)
JP (1) JP4489808B2 (en)
AT (1) ATE390542T1 (en)
BR (1) BRPI0418861A (en)
DE (1) DE602004012781T2 (en)
ES (1) ES2305774T3 (en)
WO (1) WO2005116405A1 (en)

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US20110268575A1 (en) * 2008-12-19 2011-11-03 Volvo Aero Corporation Spoke for a stator component, stator component and method for manufacturing a stator component
US8430627B2 (en) * 2009-10-29 2013-04-30 Alstom Technology Ltd Gas turbine exhaust strut refurbishment
US20120243970A1 (en) * 2009-12-17 2012-09-27 Anders Hellgren Arrangement and method for closed flow cooling of a gas turbine engine component
EP2788585B1 (en) 2011-12-08 2018-11-21 GKN Aerospace Sweden AB Gas turbine engine component
JP5934806B2 (en) * 2011-12-20 2016-06-15 ゲーコーエヌ エアロスペース スウェーデン アーベー Gas turbine engine component manufacturing method
US9689312B2 (en) 2011-12-22 2017-06-27 Gkn Aerospace Sweden Ab Gas turbine engine component
WO2013095211A1 (en) 2011-12-23 2013-06-27 Volvo Aero Corporation Support structure for a gas turbine engine
JP5933749B2 (en) 2011-12-23 2016-06-15 ゲーコーエヌ エアロスペース スウェーデン アーベー Gas turbine engine components
JP6039059B2 (en) * 2012-05-02 2016-12-07 ゲーコーエヌ エアロスペース スウェーデン アーベー Gas turbine engine support structure
EP2861847B1 (en) * 2012-06-15 2020-03-25 United Technologies Corporation High durability turbine exhaust case
JP6189432B2 (en) * 2012-07-03 2017-08-30 ゲーコーエヌ エアロスペース スウェーデン アーベー Support structure for gas turbine engine
US10221707B2 (en) * 2013-03-07 2019-03-05 Pratt & Whitney Canada Corp. Integrated strut-vane
US20150044046A1 (en) * 2013-08-07 2015-02-12 Yevgeniy Shteyman Manufacturing method for strut shield collar of gas turbine exhaust diffuser
US9835038B2 (en) 2013-08-07 2017-12-05 Pratt & Whitney Canada Corp. Integrated strut and vane arrangements
US9556746B2 (en) 2013-10-08 2017-01-31 Pratt & Whitney Canada Corp. Integrated strut and turbine vane nozzle arrangement
WO2015130425A2 (en) * 2014-02-03 2015-09-03 United Technologies Corporation Gas turbine engine cooling fluid composite tube
US9702267B2 (en) 2014-10-15 2017-07-11 Pratt & Whitney Canada Corp. Engine structure assembly procedure
US10655482B2 (en) * 2015-02-05 2020-05-19 Rolls-Royce Corporation Vane assemblies for gas turbine engines
US9909434B2 (en) 2015-07-24 2018-03-06 Pratt & Whitney Canada Corp. Integrated strut-vane nozzle (ISV) with uneven vane axial chords
JP6546481B2 (en) * 2015-08-31 2019-07-17 川崎重工業株式会社 Exhaust diffuser
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US10443451B2 (en) 2016-07-18 2019-10-15 Pratt & Whitney Canada Corp. Shroud housing supported by vane segments
DE102016217320A1 (en) * 2016-09-12 2018-03-15 Siemens Aktiengesellschaft Gas turbine with separate cooling for turbine and exhaust housing
GB201707103D0 (en) * 2017-05-04 2017-06-21 Rolls Royce Plc Vane arrangement for a gas turbine engine
GB201707101D0 (en) * 2017-05-04 2017-06-21 Rolls Royce Plc Vane arrangement for a gas turbine engine
CN107524523B (en) * 2017-08-17 2020-06-02 中国科学院工程热物理研究所 Light-weight force-transmission support plate structure and casing with same
US11242762B2 (en) * 2019-11-21 2022-02-08 Raytheon Technologies Corporation Vane with collar

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US2463340A (en) * 1945-02-22 1949-03-01 Wiberg Oscar Anton Axial flow turbine blade structure
US4883216A (en) * 1988-03-28 1989-11-28 General Electric Company Method for bonding an article projection
US5056738A (en) * 1989-09-07 1991-10-15 General Electric Company Damper assembly for a strut in a jet propulsion engine
JPH05321694A (en) * 1992-05-26 1993-12-07 Ishikawajima Harima Heavy Ind Co Ltd Manufacture of bearing frame
US5284011A (en) * 1992-12-14 1994-02-08 General Electric Company Damped turbine engine frame
US5865364A (en) * 1996-12-24 1999-02-02 United Technologies Corporation Process for linear friction welding
US6045325A (en) * 1997-12-18 2000-04-04 United Technologies Corporation Apparatus for minimizing inlet airflow turbulence in a gas turbine engine
DE19922012C1 (en) * 1999-05-12 2000-10-19 Mtu Muenchen Gmbh Rotor unit machining takes measurements of the actual surfaces at the fused joint for the flash to be removed and a nominal surface structure is machined from stored data to give the required flow characteristics
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow

Also Published As

Publication number Publication date
JP4489808B2 (en) 2010-06-23
WO2005116405A1 (en) 2005-12-08
DE602004012781D1 (en) 2008-05-08
ATE390542T1 (en) 2008-04-15
US20070140845A1 (en) 2007-06-21
US7544040B2 (en) 2009-06-09
JP2008500488A (en) 2008-01-10
ES2305774T3 (en) 2008-11-01
EP1753938B1 (en) 2008-03-26
EP1753938A1 (en) 2007-02-21
DE602004012781T2 (en) 2009-04-16

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Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 3A ANUIDADES

B08H Application fees: decision cancelled [chapter 8.8 patent gazette]

Free format text: REFERENTE AO DESPACHO 8.6 DA RPI 2082 DE 30/11/2010.

B09A Decision: intention to grant [chapter 9.1 patent gazette]
B11D Dismissal acc. art. 38, par 2 of ipl - failure to pay fee after grant in time